* *
* FGFS Reconfigurable Aircraft Flight Model *
* Input File Documentation *
-* Version 0.63, March 17, 2000 *
+* Version 0.64, March 28, 2000 *
* *
* Authors: *
-* Jeff Scott (jscott@uiuc.edu) *
+* Jeff Scott (jscott@mail.com) *
* Bipin Sehgal (bsehgal@uiuc.edu) *
* Michael Selig (m-selig@uiuc.edu) *
* Dept of Aero and Astro Engineering *
* *
************************************************
-
+
**********************************************************************
This documentation includes:
- Required and optional input lines.
- Input line formats and conventions.
-Viewing this file in emacs makefile-mode with color makes this file
-easier to read.
+ Viewing this file in emacs makefile-mode with color makes this file
+ easier to read.
**********************************************************************
**********************************************************************
| Optional data
| Sometimes indicates a feature not yet used,
but proposed convention is indicated nevertheless.
+ <...> Value or file name to be placed here
|| Input line disabled
|| Option disabled
... Repeat similar data
Cl Aerodynamic l-moment quantities (lateral)
Cn Aerodynamic n-moment quantities (lateral)
|gear Landing gear model quantities
-ice Aircraft icing model parameters
-record Record desired quantities to the file: uiuc_record.dat
+ice Icing model parameters
+record Record desired quantites to file
As each line of the input file is read, the code recognizes the
keyword, enters the appropriate switch statement in the code, and
Several of these variable names are not currently used.
1) variable class
-_ denotes stability derivative to be multiple by something
+_ denotes stability derivative to be multiplied by something
f "function of" (indicates an m*n matrix data table is given)
2) timing data (global simulator variables)
Re Reynolds number []
4) atmosphere properties
-Density air density [slug/ft^3]
+Density air density [slug/ft^3]
5) geometric variables
bw wingspan [ft]
|muGear gear rolling friction coef [?]
|strutLength gear strut length [ft]
-12) icing model paramters
+12) icing model parameters
iceTime time when icing begins [s]
transientTime time period over which eta increases to final [s]
eta_final icing severity factor at end of transient time [-]
max maximum
min minimum
-(3) | (OPTIONAL DATA)
+(3) | [OPTIONAL DATA]
=====================
An input line may also be used to provide optional data that
values or data files may be provided if the code is written to use
them.
-(4) # (COMMENTS)
+(4) # [COMMENTS]
================
Appended comments should be provided with each input line to indicate
**********************************************************************
**********************************************************************
-IV. Definitions of Input Lines Currently Available:
+IV. Input Line Definitions:
-Of all the possible permutation of variable names described above in
-section II, only some are currently implemented in the code. These
-are described below. Comments, denoted by '#,' are used to define the
+Of all the possible permutations of variable names described above in
+section II, only some are curently implemented in the code. These are
+described below. Comments, denoted by '#,' are used to define the
lines and to indicate examples of the data if additional clarity is
needed for unique situations. Again, those lines beginning with '|'
are not currently implemented in the code, but indicate planned
mass I_zz <I_zz> # [slug-ft^2] yaw inertia ls_generic.h
mass I_xz <I_xz> # [slug-ft^2] lateral cross inertia ls_generic.h
-|engine thrust <thrustMax> <thrustMin> # [lb] max/min engine thrust uiuc_aircraft.h
-engine simpleSingle <sSMaxThrust> # [lb] simple single engine uiuc_aircraft.h
-engine c172 # use Cessna 172 engine model of Tony Peden
+
+# maximum and minimum engine thrust [lb] uiuc_aircraft.h
+|engine thrust <thrustMax> <thrustMin>
+
+# simple single engine maximum thrust [lb] uiuc_aircraft.h
+engine simpleSingle <simpleSingleMaxThrust>
+
+engine c172 # use Cessna 172 engine model of Tony Peden
+
CL CLo <CLo> # [] lift coef for all angles = 0 uiuc_aircraft.h
CL CL_a <CL_a> # [/rad] lift curve slope, d(CL)/d(alpha) uiuc_aircraft.h
|CL CLfCT <CLfCT.dat> # CL(thrust coef) uiuc_aircraft.h
|CL CLfRe # CL(Reynolds #), equation uiuc_aircraft.h
|CL CL_afaM <CL_afaM.dat> # CL_alpha(alpha,Mach #) uiuc_aircraft.h
-# there are examples that might later be included in the code
+ # these are sample examples that might be used in later versions of the code
+
# note that CD terms must come after CL for induced drag to be computed
CD CDo <CDo> # [] drag coef for all angles = 0 uiuc_aircraft.h
Cm Cm_de <Cm_de> # [/rad] d(Cm)/d(de) uiuc_aircraft.h
|Cm Cmfa <Cmfa.dat> # [] Cm(alpha) uiuc_aircraft.h
Cm Cmfade <Cmfade.dat> # [] Cm(alpha,delta_e) uiuc_aircraft.h
+
# Cm(alpha,delta_e), conversion for Cm, for alpha, for delta_e [] uiuc_aircraft.h
Cm Cmfade <Cmfade.dat> <conversion1> <conversion2> <conversion3>
+
CY CYo <CYo> # [] side-force coef for all angles=0 uiuc_aircraft.h
CY CY_beta <CY_beta> # [/rad] d(CY)/d(beta) uiuc_aircraft.h
CY CY_p <CY_p> # [/rad] d(CY)/d(p) uiuc_aircraft.h
projects / flightgear.git / blobdiff